CN113799970A - Lifting surface structure of integrated ducted fan - Google Patents
Lifting surface structure of integrated ducted fan Download PDFInfo
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- CN113799970A CN113799970A CN202111264812.3A CN202111264812A CN113799970A CN 113799970 A CN113799970 A CN 113799970A CN 202111264812 A CN202111264812 A CN 202111264812A CN 113799970 A CN113799970 A CN 113799970A
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- fan
- duct
- aileron
- lifting
- wing surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
Abstract
The invention discloses a lifting surface structure of an integrated ducted fan, which comprises: the lower wing surface is arranged at the symmetrical position of the lower side of the upper wing surface, and a duct and a connecting wall plate with a special curved surface structure on the inner surface are arranged at equal intervals on the inner sides of the upper wing surface and the lower wing surface; a fan body is arranged in each duct, and the fan body consists of a propeller hub, rotor blades and a stator; an upper aileron located on a rear side of the upper airfoil surface. This lifting surface structure of integrated ducted fan is convenient for reduce the resistance of lifting surface, makes the aircraft realize taking off and landing perpendicularly, horizontal flight and the steady conversion between taking off and landing perpendicularly and the horizontal flight state, is convenient for reduce aircraft driving system noise simultaneously, improves the operation security, is convenient for make the aircraft all can obtain effectual control at the flight state of difference to be convenient for improve the flight efficiency of aircraft, improve the lift-drag ratio of cruising, reduce the consumption of the energy.
Description
Technical Field
The invention relates to the technical field of airplane aerodynamics, in particular to a lifting surface structure of an integrated ducted fan.
Background
The urban manned aircraft and the unmanned transport plane in a special scene have high requirements on the take-off and landing performance of the aircraft, the vertical take-off and landing can reduce the requirements on a take-off and landing site, the electric energy and the motors are used as energy sources and power systems of the aviation aircraft, the distributed power system can be easily realized, the aircraft can be more easily vertically taken off and landed, the flight performance and the control quality of the aircraft can be improved, the aircraft of the existing distributed power system usually adopts a plurality of motors to drive open propellers, so that the open propellers drive the aircraft, the propellers can fully utilize the slipstream of the propellers to improve the lift force of wings, reduce the area of the aircraft wing and reduce the structural weight.
However, in the process of using the open propeller to drive the aircraft, because the open propeller usually increases the efficiency by increasing the diameter of the propeller to reduce the power consumption, the rotating speed of the propeller is limited, thereby limiting the improvement of performance, and the size and the layout of the aircraft usually limit the further increase of the size of the propeller, so that the use of the open propeller brings safety problems to the aircraft, and noise in flight is increased, and in the process of converting the vertical take-off and landing of the aircraft and the vertical take-off and landing to the flat flight, the flight speed of the aircraft is low, the aerodynamic force cannot generate enough aerodynamic force on a movable surface, thereby easily changing the flight attitude, therefore, a lifting surface structure of the integrated ducted fan is provided, so as to solve the problems provided in the above.
Disclosure of Invention
The invention aims to provide a lifting surface structure of an integrated ducted fan, which aims to solve the problems that in the process of using an open propeller to drive an aircraft, the open propeller often increases the diameter of the propeller to improve efficiency and reduce power consumption, so the rotating speed of the propeller is limited to limit the improvement of performance, the size and the layout of the aircraft often limit the further increase of the size of the propeller, the open propeller is used, the safety problem is brought to the use of the aircraft, the noise in flight is increased, and in the process of converting vertical take-off and landing of the aircraft and from vertical take-off and landing to flat flight, the flight speed of the aircraft is low, the aerodynamic force cannot generate enough aerodynamic force on a movable surface, and the flight attitude is easy to change.
In order to achieve the purpose, the invention provides the following technical scheme: a lifting surface structure of an integrated ducted fan, comprising:
the lower sides of the upper wing surfaces are symmetrically provided with lower wing surfaces, and ducts and a connecting wall plate with a curved surface structure on the inner surface are arranged on the inner sides of the upper wing surfaces and the lower wing surfaces at equal intervals;
the fan body is placed in each duct and consists of a propeller hub, fan blades and a stator;
and the lower aileron is positioned at the rear side of the lower airfoil surface and is arranged at the lower side of the upper aileron.
Preferably, the upper wing surface, the lower wing surface and the connecting wall plate are of a welding integrated structure, a plurality of ducts are formed on the inner sides of the upper wing surface, the lower wing surface and the connecting wall plate, the outer sections of the upper wing surface and the lower wing surface are of modified low-speed wing shapes, and the inner sides of the middle sections of the upper wing surface, the lower wing surface and the connecting wall plate are of equal-circle sections.
Preferably, the inner section of the duct is circular, the circular shape gradually transits to the rectangular inlet and outlet from front to back, the front edge of the upper half part of the front part of the wing of the duct is an upward convex circular arc, and the fan body is installed on the inner side of the duct.
Preferably, the fan blade and the stator are both fixedly connected with the hub, and the fan blade and the stator are both symmetrically provided with multiple groups around the hub center.
Preferably, the upper aileron and the lower aileron are symmetrically arranged, and the upper aileron and the lower aileron are respectively and rotatably connected with the upper airfoil surface and the lower airfoil surface through mounting shafts.
Compared with the prior art, the invention has the beneficial effects that: the lifting surface structure of the integrated ducted fan is convenient for reducing the resistance of the lifting surface, so that the aircraft can realize vertical landing and horizontal flight and stable conversion between the states of the vertical landing and the horizontal flight, and simultaneously is convenient for reducing the noise of a power system of the aircraft, improving the operation safety and effectively controlling the aircraft in different flight states, thereby being convenient for improving the flight efficiency of the aircraft, improving the cruise lift-drag ratio and reducing the energy consumption;
1. the fan is provided with an upper wing surface, a lower wing surface, a connecting wall plate and a duct, because the inner sides of the upper wing surface, the lower wing surface and the connecting wall plate are provided with a plurality of ducts with fan bodies arranged on the inner sides, each fan body is composed of a hub, a plurality of groups of fan blades and stators which are arranged in the central symmetry of the hub, and the outer sections of the upper wing surface and the lower wing surface are modified low-speed wing profiles, and the inner sides of the middle sections of the upper wing surface and the lower wing surface are equicircular sections, therefore, the fan body can accelerate the internal airflow of the upper airfoil surface and the lower airfoil surface and the airflow on the surface of the upper airfoil surface and the lower airfoil surface which are supported and connected with the wallboard, the suction force of the front edge of the duct is generated to increase the efficiency of the power system and reduce the resistance of the lifting surface, therefore, the aircraft can realize the stable conversion between the states of vertical take-off and landing, horizontal flight and vertical take-off and landing and horizontal flight, is convenient for reducing the noise of the power system of the aircraft, and improves the operation safety.
2. The aircraft is provided with an upper wing surface, a lower wing surface, a mounting shaft and an upper aileron, and the rear sides of the upper wing surface and the lower wing surface are respectively connected with the upper aileron and the lower aileron through the mounting shaft, so that the aircraft is convenient to provide enough lift force for the aircraft to maintain the power required by the vertical lifting and landing of the aircraft and the lift force required by the flat flight, the aircraft can be effectively controlled in different flight states, the flight efficiency of the aircraft is convenient to improve, the cruise lift-drag ratio is improved, and the energy consumption is reduced.
Drawings
FIG. 1 is a schematic front perspective view of the present invention;
FIG. 2 is a schematic rear perspective view of the present invention;
FIG. 3 is a schematic side view of a cross-sectional configuration of the upper airfoil and the lower airfoil of the present invention;
FIG. 4 is a schematic view of the shape and structure of the duct of the present invention;
FIG. 5 is a schematic view of the entire structure of the fan body according to the present invention;
FIG. 6 is a schematic structural view of the upper and lower ailerons of the present invention in an up-deflected state;
FIG. 7 is a schematic view of the downward deflection of the upper and lower ailerons of the present invention;
FIG. 8 is a schematic view of the inboard deflection of the upper and lower ailerons of the present invention.
In the figure: 1. an upper airfoil surface; 2. a lower airfoil surface; 3. connecting the wall plates; 4. a duct; 401. a circular shape; 402. a rectangular inlet and outlet; 403. an upwardly convex arc; 5. a fan body; 501. a hub; 502. a fan blade; 503. a stator; 6. a profiled low speed airfoil; 7. an equal circle section; 8. installing a shaft; 9. an upper flap; 10. and a lower aileron.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-8, the present invention provides a technical solution: a lifting surface structure of an integrated ducted fan comprises an upper wing surface 1, a lower wing surface 2, a connecting wall plate 3, a duct 4, a circle 401, a rectangular inlet and outlet 402, an upward convex circular arc 403, a fan body 5, a propeller hub 501, fan blades 502, a stator 503, a modified low-speed wing section 6, an equal-circle section 7, a mounting shaft 8, an upper aileron 9 and a lower aileron 10;
when the lifting surface structure of the integrated ducted fan is used, as shown in fig. 1, 2, 3, 4 and 5, the integrated ducted lifting surface comprises an upper wing surface 1, a lower wing surface 2 is symmetrically arranged on the lower side of the upper wing surface 1, and a duct 4 and a connecting wall plate 3 with a curved surface structure on the inner surface are arranged on the inner sides of the upper wing surface 1 and the lower wing surface 2 at equal intervals;
the fan body 5, one fan body 5 is placed in each duct 4, and the fan body 5 is composed of a hub 501, fan blades 502 and a stator 503; the number of the ducts 4 can be adjusted according to the lift demand and the power demand, the cross section of the inside of each duct 4 is circular 401, the duct 4 gradually transits to a rectangular inlet/outlet 402 from front to back, the front edge of the upper half part of the front part of each duct 4 is an upward convex arc 403, the outer sections of the upper airfoil surface 1 and the lower airfoil surface 2 are modified low-speed airfoil profiles 6 which have good stall characteristics, and the inner sections of the middle sections of the upper airfoil surface 1 and the lower airfoil surface 2 are equal-circular sections 7, so that a constant gap is kept between the fan blade 502 and the connecting wall plate 3 when the fan blade 502 rotates, and the air flow passing through the fan blade 502 in a rotation period is stable;
referring to fig. 1, 2, 3 and 4, the cross section of the duct 4 has a larger inlet area, so as to ensure sufficient air inflow under different working conditions, and the shape is modified according to the flow field characteristics, so that under different flow coefficients, the flow of the lips of the duct 4 is not obviously separated, the middle section of the cross section of the duct 4 is an equicircular cross section 7, so that a constant gap is kept between the fan blade 502 and the connecting wall plate 3 when the fan blade rotates, the air flow passing through the blade in a rotation period is stable, because the outlet of the duct 4 is approximately rectangular, the cross section of the duct 4 is gradually reduced after passing through the fan body 5, so that the area of the outlet cross section is not rapidly enlarged, and further, the back pressure of the outlet of the fan body 5 is not increased too fast, so that the air flow separation in the duct 4 is caused, therefore, the twist angles of different sections of the propeller can be adjusted according to the air flow velocity and angle of the fan body 5 in the duct 4 under different working conditions, the device can generate effective thrust in a wider speed adaptation range, and not only can meet the requirement of high thrust in vertical take-off and landing, but also can meet the requirement of high efficiency in cruising;
as shown in fig. 1, 2, 6, 7 and 8, the upper and lower ailerons 9 and 10 are respectively mounted on the rear sides of the upper and lower wing surfaces 1 and 2, the upper and lower ailerons 9 and 10 can deflect up and down around the mounting shaft 8, when the ducted lifting surface works, the upper and lower ailerons 9 and 10 simultaneously deflect upwards or downwards, and the lift force and the pitch moment of the lifting surface and the lower lifting surface are changed, so that the aircraft can generate pitching and rolling motions, even if the moving speed of the lifting surface is very low and relatively static relative to the air at infinity, when the upper and lower ailerons 9 and 10 deflect upwards, the pressure distribution of the rear edge of the lifting surface can be changed through ducted jet flow, so as to generate lift force change, generate operating moment for the aircraft, the upper and lower ailerons 9 and 10 can also simultaneously deflect inwards when the fan body 5 works, so as to change the outlet area of the duct 4 to change the air flow rate and static pressure, thereby changing the thrust of the duct and adapting to the flight states with different speeds;
referring to fig. 1 and 2, the lifting surface of the integrated ducted fan can bear the load generated by the weight, inertia force and pulling force of the power system by being fixed inside the duct 4 through the electrodynamic force fan body 5, a certain installation angle is formed between the stator 503 and the axis of the engine by being positioned behind the fan blade 502, the installation angle is determined according to the included angle between the airflow after the fan and the axis, the effect of rectifying the wake flow of the propeller can be achieved, the rotation speed of the wake flow is reduced, the early separation of the wake flow of the propeller is avoided, simultaneously, the noise of the propeller can be reduced by generating extra thrust through the relative angle with the wake flow, the lifting surface can take away a part of the ambient air through the viscous action in the state of large attack angle, such as the process of the conversion of the vertical takeoff and landing state of the aircraft or the flat flight of the aircraft in the state of large attack angle, so that the separation of the upper surface of the lifting surface in the state of large attack angle can be delayed, the lift force for maintaining the flight of the aircraft can be generated by the lift surface within a larger attack angle range, so that the wing area can be reduced, the structure weight can be reduced, and the flight efficiency can be improved.
The details which are not described in the present specification belong to the prior art which is well known to those skilled in the art, the standard parts used in the present invention can be purchased from the market, the special-shaped parts can be customized according to the description and the description of the drawings, the specific connection mode of each part adopts the conventional means of bolts, rivets, welding and the like which are mature in the prior art, the machinery, parts and equipment adopt the conventional type in the prior art, the circuit connection adopts the conventional connection mode in the prior art, and the details which are not described in the present specification belong to the prior art which is well known to those skilled in the art.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.
Claims (6)
1. A lifting surface structure of an integrated ducted fan, comprising:
the device comprises an upper wing surface (1), wherein lower wing surfaces (2) are symmetrically arranged on the lower side of the upper wing surface (1), and ducts (4) and a connecting wall plate (3) with a curved surface structure on the inner surface are arranged on the inner sides of the upper wing surface (1) and the lower wing surfaces (2) at equal intervals;
the fan comprises fan bodies (5), wherein one fan body (5) is arranged in each duct (4), and each fan body (5) consists of a hub (501), fan blades (502) and a stator (503);
the upper aileron (9) is positioned at the rear side of the upper airfoil surface (1), and the lower side of the upper aileron (9) is provided with a lower aileron (10) positioned at the rear side of the lower airfoil surface (2).
2. The integrated ducted fan lifting surface structure according to claim 1, wherein: the upper wing surface (1), the lower wing surface (2) and the connecting wall plate (3) are of a welding integrated structure, a plurality of ducts (4) are formed in the inner sides of the upper wing surface (1), the lower wing surface (2) and the connecting wall plate (3), the outer sections of the upper wing surface (1) and the lower wing surface (2) are low-speed wing sections (6) which are subjected to shape modification, and the inner sides of the middle sections of the upper wing surface (1), the lower wing surface (2) and the connecting wall plate (3) are equal-circle sections (7).
3. The integrated ducted fan lifting surface structure according to claim 2, wherein: the inner section of the duct (4) is circular (401), the circular (401) gradually transits to a rectangular inlet and outlet (402) from front to back, the front edge of the upper half part of the front part of the wing of the duct (4) is an upward convex circular arc (403), and a fan body (5) is installed on the inner side of the duct (4).
4. The integrated ducted fan lifting surface structure according to claim 1, wherein: the fan blade (502) and the stator (503) are fixedly connected with the hub (501), and the fan blade (502) and the stator (503) are symmetrically arranged in multiple groups around the center of the hub (501).
5. The integrated ducted fan lifting surface structure according to claim 1, wherein: the upper aileron (9) and the lower aileron (10) are symmetrically arranged, and the upper aileron (9) and the lower aileron (10) are respectively connected with the upper airfoil surface (1) and the lower airfoil surface (2) in a rotating way through a mounting shaft (8).
6. The integrated ducted fan lifting surface structure according to claim 1, wherein: the working principle is as follows: the upper wing surface (1), the lower wing surface (2) and the connecting wall plate (3) form a duct (4) which is used for accommodating a fan body (5) formed by a hub (501), fan blades (502) and a stator (503), the number of the ducts (4) can be adjusted according to the lift force requirement and the power requirement, the outer sections of the upper wing surface (1) and the lower wing surface (2) are modified low-speed wing profiles (6) which have good stall characteristics, the inner sections of the middle sections of the upper wing surface (1) and the lower wing surface (2) are equal-circle sections (7), so that a constant gap is kept between the fan blades (502) and the connecting wall plate (3) when the fan blades (502) rotate, and the air flow passing through the fan blades (502) in a rotation period is stable;
the cross section of the duct (4) has a larger inlet area, so that enough air inflow is ensured under different working conditions, meanwhile, the shape modification is carried out according to the flow field characteristics, the flow of the lip of the duct (4) can not be obviously separated under different flow coefficients, the middle section of the cross section of the duct (4) is an equicircular section (7), so that a constant gap is kept between the rotor blade (502) and the connecting wall plate (3) when the rotor blade rotates, the air flow passing through the blade in a rotating period is stable, and the cross section of the duct (4) is gradually reduced after passing through the fan body (5) because the outlet of the duct (4) is approximately rectangular, so that the area of the outlet section can not be rapidly enlarged, further, the back pressure of the outlet of the fan body (5) can not be increased too fast, the air flow separation in the duct (4) can not be caused, and the torsion angles of different sections of the propeller can be adjusted according to the air flow velocity and angle of the fan body (5) in the duct (4) under different working conditions, the thrust can be effectively generated in a wider speed adaptation range;
when the ducted lifting surface works, the upper aileron (9) and the lower aileron (10) deflect upwards or downwards simultaneously, and the lifting force and the pitching moment of the lifting surface and the lower lifting surface are changed, so that the aircraft generates pitching and rolling motions, even if the moving speed of the lifting surface is very low and is still relative to the air at infinite distance, when the upper aileron (9) deflects downwards or the lower aileron (10) deflects upwards, the pressure distribution of the rear edge of the lifting surface can be changed through ducted jet flow, the lifting force change is generated, the control moment is generated on the aircraft, the upper aileron plate (9) and the lower aileron plate (10) can also deflect inwards simultaneously when the fan body (5) works, so that the outlet area of the duct (4) is changed to change the air flow rate and the static pressure, the thrust of the duct is changed, and the air flow state of different speeds is adapted;
the lifting surface of the integrated ducted fan is fixed inside a duct (4) through an electrodynamic force fan body (5) to bear the load generated by the weight, the inertia force and the pulling force of a power system, a stator (503) is positioned behind a fan blade (502) to form a certain installation angle with the axis of an engine, the installation angle is determined according to the included angle between the airflow behind the fan and the axis, the rectification effect on the wake flow of a propeller can be achieved, the rotation speed of the wake flow is reduced, the early separation of the wake flow of the propeller is avoided, meanwhile, extra thrust is generated through the relative angle of the wake flow and the propeller, the noise of the propeller can be reduced, the lifting surface is in a large attack angle state, the separation of the upper surface of the lifting surface in the large attack angle state can be delayed, and the lifting surface can generate the lifting force for maintaining the flight of an aircraft in a large attack angle range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111264812.3A CN113799970A (en) | 2021-10-28 | 2021-10-28 | Lifting surface structure of integrated ducted fan |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111264812.3A CN113799970A (en) | 2021-10-28 | 2021-10-28 | Lifting surface structure of integrated ducted fan |
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| CN113799970A true CN113799970A (en) | 2021-12-17 |
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| CN202111264812.3A Pending CN113799970A (en) | 2021-10-28 | 2021-10-28 | Lifting surface structure of integrated ducted fan |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476093A (en) * | 2022-03-17 | 2022-05-13 | 北京航空航天大学 | Distributed electric propulsion aircraft and control method thereof |
| CN114572405A (en) * | 2022-03-08 | 2022-06-03 | 南京航空航天大学 | Novel paddle fan-type rotor with foldable back row of paddles and layout design of novel paddle fan-type rotor |
-
2021
- 2021-10-28 CN CN202111264812.3A patent/CN113799970A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572405A (en) * | 2022-03-08 | 2022-06-03 | 南京航空航天大学 | Novel paddle fan-type rotor with foldable back row of paddles and layout design of novel paddle fan-type rotor |
| CN114476093A (en) * | 2022-03-17 | 2022-05-13 | 北京航空航天大学 | Distributed electric propulsion aircraft and control method thereof |
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